Bigelow Aerospace has two inflatables on orbit (Genesis I and Genesis II) with plans for attaching the BEAM module to the ISS. These are precursors to a full scale station, based on multiple (3?) BA-330 full size modules.
The plan is for solar panels at the ends of the BA-330 modules. They seem like they will have lower power output than the ISS, based simply on size. (Assuming efficiency is vaguely similar, even though the panels will be 20 years newer). Ignoring the power issue for a moment, I am curious about the heat rejection problem.
In space, paradoxically, it would seem, getting rid of heat is one of the harder problems. Between the 90 min day/night cycle, the temperature cycling, and the amount of heat humans and equipment put out, getting heat OUT of the station is a major design issue.
The ISS has some very large radiators, the ammonia cooling loop system, that have made the news in past years for a variety of problems. (MMOD on one of the radiatiors, ammonia leaks, failed pumps, etc).
How does Bigelow plan to handle the heat rejection issue? None of the images I have seen, show obvious large radiators.